WO2013043076A1 - Brûleur et procédé d'alimentation en combustible d'un brûleur - Google Patents

Brûleur et procédé d'alimentation en combustible d'un brûleur Download PDF

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Publication number
WO2013043076A1
WO2013043076A1 PCT/RU2011/000724 RU2011000724W WO2013043076A1 WO 2013043076 A1 WO2013043076 A1 WO 2013043076A1 RU 2011000724 W RU2011000724 W RU 2011000724W WO 2013043076 A1 WO2013043076 A1 WO 2013043076A1
Authority
WO
WIPO (PCT)
Prior art keywords
combustor
center body
shroud
liner
cap
Prior art date
Application number
PCT/RU2011/000724
Other languages
English (en)
Inventor
Almaz Kamilevich Valeev
James Harold WESTMORELAND, III
Keith C. BELSOM
John Alfred SIMO
Original Assignee
General Electric Company
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Company filed Critical General Electric Company
Priority to JP2014531757A priority Critical patent/JP6050821B2/ja
Priority to PCT/RU2011/000724 priority patent/WO2013043076A1/fr
Priority to CH00425/14A priority patent/CH707282B1/de
Priority to DE112011105655.9T priority patent/DE112011105655B4/de
Priority to US14/344,336 priority patent/US9388987B2/en
Publication of WO2013043076A1 publication Critical patent/WO2013043076A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L7/00—Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/045—Air inlet arrangements using pipes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07002—Injecting inert gas, other than steam or evaporated water, into the combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07008—Injection of water into the combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07009—Injection of steam into the combustion chamber

Definitions

  • the present invention generally involves a combustor and method for supplying fuel to the combustor.
  • a typical gas turbine used to generate electrical power includes an axial compressor at the front, one or more combustors around the middle, and a turbine at the rear.
  • Ambient air may be supplied to the compressor, and rotating blades and stationary vanes in the compressor progressively impart kinetic energy to the working fluid (air) to produce a compressed working fluid at a highly energized state.
  • the compressed working fluid exits the compressor and flows through one or more nozzles into a combustion chamber in each combustor where the compressed working fluid mixes with fuel and ignites to generate combustion gases having a high temperature and pressure.
  • the combustion gases expand in the turbine to produce work. For example, expansion of the combustion gases in the turbine may rotate a shaft connected to a generator to produce electricity.
  • the combustion gases exiting the turbine include varying amounts of nitrous oxides, carbon monoxide, unburned hydrocarbons, and other undesirable emissions, with the actual amount of each emission dependent on design and operating parameters.
  • the design length of the combustor directly effects the amount of time that the fuel-air mixture remains in the combustor.
  • a longer residence time of the fuel-air mixture in the combustor generally increases the nitrous oxide levels, while a shorter residence time of the fuel-air mixture in the combustor generally increases the carbon monoxide and unburned hydrocarbon levels.
  • the operating level of the combustor directly influences the emissions content on the combustion gases.
  • One embodiment of the present invention is a combustor that includes a cap, a liner extending downstream from the cap, and a transition piece extending downstream from the liner.
  • a combustion chamber is located downstream from the cap and at least partially defined by the cap and the liner.
  • a secondary nozzle is circumferentially arranged around at least one of the liner or the transition piece.
  • the secondary nozzle includes a center body that extends from a casing surrounding the combustor through at least one of the liner or the transition piece, a fluid passage through the center body, a shroud circumferentially surrounding at least a portion of the center body, and an annular passage between the center body and the shroud.
  • Another embodiment of the present invention is a combustor that includes a cap, a primary nozzle radially disposed in the cap, a liner extending downstream from the cap, a combustion chamber downstream from the cap and at least partially defined by the cap and the liner, and a transition piece extending downstream from the liner.
  • a secondary nozzle is circumferentially arranged around and passes through at least one of the liner or the transition piece.
  • the secondary nozzle includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding at least a portion of the center body, and an annular passage between the center body and the shroud.
  • the present invention may also include a method for supplying fuel to a combustor that includes flowing a first fuel through a primary nozzle radially disposed in a breech end of the combustor and flowing a second fuel through a secondary nozzle circumferentially arranged around and passing through at least one of a liner or a transition piece.
  • the secondary nozzle includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding at least a portion of the center body, and an annular passage between the center body and the shroud.
  • FIG. 1 is a simplified cross-section of an exemplary combustor according to a first embodiment of the present invention
  • FIG. 2 is a enlarged view of an embodiment of a secondary nozzle shown in Fig. 1 ;
  • FIG. 3 is a simplified cross-section of a combustor according to a second embodiment of the present invention.
  • FIG. 4 is an enlarged view of an embodiment of a secondary nozzle shown in Fig. 3;
  • FIG. 5 is an enlarged view of an alternate embodiment of a secondary nozzle shown in Fig. 3.
  • Various embodiments of the present invention include a combustor having primary and secondary nozzles.
  • the primary nozzles may be located at a breech end of the combustor, and the secondary nozzles may be located peripherally around a combustion chamber.
  • the primary and secondary nozzles provide a staged supply of fuel premixed with compressed working fluid to the combustion chamber to optimize the combustion gas temperature and residence time of the fuel in the combustor.
  • FIG. 1 provides a simplified cross-section of an exemplary combustor 10, such as may be included in a gas turbine, according to one embodiment of the present invention.
  • a casing 12 may surround the combustor 10 to contain the compressed working fluid flowing to the combustor 10.
  • the combustor 10 may include one or more primary nozzles 14 radially arranged in the breech end between a cap 16 and an end cover 18.
  • the cap 16 and a liner 20 generally surround or define a combustion chamber 22 located downstream from the primary nozzles 14, and a transition piece 24 located downstream from the liner 20 connects the combustion chamber 22 to a turbine inlet 26.
  • downstream refer to the relative location of components in a fluid pathway.
  • component A is upstream from component B if a fluid flows from component A to component B.
  • component B is downstream from component A if component B receives a fluid flow from component A.
  • An impingement sleeve 28 with flow holes 30 may surround the transition piece 24 to define an annular plenum 32 between the impingement sleeve 28 and the transition piece 24.
  • the compressed working fluid may pass through the flow holes 30 in the impingement sleeve 28 to flow through the annular plenum 32 to provide convective cooling to the transition piece 24 and/or liner 20.
  • the compressed working fluid reaches the end cover 18, the compressed working fluid reverses direction to flow through the primary nozzles 14 where it mixes with fuel before igniting in the combustion chamber 22 to produce combustion gases having a high temperature and pressure.
  • the combustor 10 further includes one or more secondary nozzles 40 circumferentially arranged around the combustion chamber 22 and aligned approximately perpendicular to the primary nozzles 14.
  • the secondary nozzles 40 provide fluid communication through the transition piece 34 to the combustion chamber 22.
  • Fig. 2 provides an enlarged view of one embodiment of the secondary nozzle 40 shown in Fig. 1.
  • the secondary nozzle 40 may connect to a fluid manifold 42 located outside of the combustor 10.
  • the fluid manifold 42 may supply fuel and/or a diluent through the secondary nozzle 40 to the combustion chamber 22.
  • Possible liquid fuels supplied from the fluid manifold 42 through the secondary nozzle 40 may include light and heavy fuel oil, oil slurries, naptha, petroleum, coal tar, crude oil, and gasoline, and possible gaseous fuels supplied by the fluid manifold 42 through the secondary nozzle 40 may include blast furnace gas, carbon monoxide, coke oven gas, natural gas, methane, vaporized liquefied natural gas (LNG), hydrogen, syngas, butane, propane, and olefins.
  • Possible diluents supplied from the fluid manifold 42 through the secondary nozzle 40 may include water, steam, fuel additives, various inert gases such as nitrogen, and/or various non-flammable gases such as carbon dioxide or combustion exhaust gases.
  • the location of the fluid manifold 42 outside of the combustor 10 allows for ambient air to quickly dilute and dissipate any leaking fuel or diluent and facilitates the detection and repair of any leaks that may develop in the fluid manifold 42.
  • the secondary nozzle 40 generally includes a center body 44 that defines a fluid passage 46 that extends from the casing 12 surrounding the combustor 10 through the transition piece 24.
  • the fluid passage 46 may terminate at a plurality of ports 48 that provides fluid communication between the center body 42 and the combustion chamber 22.
  • the ports 48 may be angled with respect to an axial centerline 50 of the fluid passage 46 to impart swirl to the fluid flowing through the fluid passage 46 into the combustion chamber 22. In this manner, the center body 44, fluid passage 46, and ports 48 allow the introduction of fuel and/or diluents through the transition piece 24 to the combustion chamber 22 downstream from the primary nozzles 14.
  • the secondary nozzle 40 may further include a shroud 52 that
  • the secondary nozzle 40 may include one or more swirler vanes 58 in the annular passage 54 to impart a tangential swirl to the compressed working fluid flowing through the annular passage 54 and into the combustion chamber 22.
  • FIG. 3 provides a simplified cross-section of a second embodiment of the combustor 10
  • Fig. 4 provides an enlarged view of the secondary nozzle 40 shown in Fig. 3.
  • the combustor 10 again includes the casing 12, primary nozzles 14, cap 16, end cover 18, liner 20, combustion chamber 22, transition piece 24, and annular plenum 32 as previously described with respect to Figs. 1 and 2.
  • the secondary nozzles 40 are again circumferentially arranged around the combustion chamber 22 and aligned approximately perpendicular to each primary nozzle 14.
  • the secondary nozzles 40 again connect to the fluid manifold 42 located outside of the combustor 10 so that the fluid manifold 42 may again supply fuel and/or diluent through the secondary nozzles 40 to the combustion chamber 22.
  • the secondary nozzles 40 provide fluid communication to the combustion chamber 22 through the liner 20.
  • each secondary nozzle 40 again generally includes the center body 44, fluid passage 46, ports 48, annular passage 54, and swirler vanes 58 as previously described with respect to the embodiment shown in Fig. 2.
  • the shroud 52 generally extends continuously from the casing 12 to the liner 20.
  • the shroud 52 includes a plurality of apertures 60 that provides fluid communication through the shroud 52 to the annular passage 54. In this manner, compressed working fluid flowing through the annular plenum 32 may pass through the apertures 60 into the annular passage 54 and flow over the swirler vanes 58 into the combustion chamber 22.
  • FIG. 5 provides an enlarged view of an alternate embodiment of the secondary nozzle 40 shown in Fig. 3.
  • the swirler vanes 58 present in Fig. 4 have been removed, and the apertures 60 have been angled at least one of azimuthally or radially with respect to the axial centerline 50 of the fluid passage 46. In this manner, the angled apertures 60 impart a tangential swirl to the compressed working fluid flowing through the annular passage 54 and into the combustion chamber 22.
  • the various embodiments shown in Figs. 1-5 provide a method for supplying fuel to the combustor 10.
  • the method may include flowing a first fuel through the plurality of primary nozzles 14 radially disposed in the breech end of the combustor 10 and flowing a second fuel through the plurality of secondary nozzles 40 circumferentially arranged around and passing through at least one of the liner 20 or the transition piece 24.
  • the first and second fuels may be the same fuel or different fuel, depending on the particular design and operational needs.
  • Each secondary nozzle 40 generally includes the center body 44, the fluid passage 46 through the center body 44, the shroud 52 circumferentially surrounding at least a portion of the center body 44, and the annular passage 54 between the center body 44 and the shroud 52.
  • the method may include flowing the first fuel approximately perpendicular to the second fuel.
  • the method may include swirling the second fuel through the ports 48 and/or swirling the compressed working fluid flowing through the annular passage 54 into the combustion chamber 22.
  • the various embodiments and methods described herein may provide one or more material and/or operational benefits over existing combustors.
  • the primary and secondary nozzles 14, 40 provide a staged injection of pre-mixed fuel-air mixtures into the combustion chamber 22.
  • the staged injection of pre-mixed fuel-air mixtures may allow for more precise control of combustion gas temperatures during both high power operations as well during reduced power or turndown operations. A more precise control of combustion gas temperatures will in turn enhance the ability to reduce or control undesirable emissions produced across a wider range of combustor 10 operations.
  • the arrangement of the secondary nozzles 40 circumferentially around the combustion chamber 22 allows for the fluid manifold 42 to be located outside of the combustor 10.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

L'invention concerne un brûleur (10) comprenant une calotte (16), un chemisage (20), une pièce de transition (24) et une chambre de combustion (22) située en aval de la calotte (16) et définie par la calotte et le chemisage. Une tuyère secondaire (40) disposée de façon circonférentielle autour du chemisage (20) ou de la pièce de transition (24) comprend un corps central, un passage de fluide traversant le corps central, un carénage entourant de façon circonférentielle le corps central, et un passage annulaire entre le corps central et le carénage. Un procédé d'alimentation en combustible d'un brûleur (10) comprend les étapes consistant à faire circuler du combustible à travers une tuyère primaire disposée radialement dans une extrémité de culasse du brûleur et à faire circuler du combustible à travers une tuyère secondaire (40) disposée de façon circonférentielle autour d'un chemisage (20) et/ou d'une pièce de transition et passant à travers celui-ci et/ou celle-ci. La tuyère secondaire (40) comprend un corps central, un passage de fluide traversant le corps central, un carénage entourant de façon circonférentielle au moins une partie du corps central (44), et un passage annulaire entre le corps central et le carénage.
PCT/RU2011/000724 2011-09-22 2011-09-22 Brûleur et procédé d'alimentation en combustible d'un brûleur WO2013043076A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
JP2014531757A JP6050821B2 (ja) 2011-09-22 2011-09-22 燃焼器及び燃焼器に燃料を供給する方法
PCT/RU2011/000724 WO2013043076A1 (fr) 2011-09-22 2011-09-22 Brûleur et procédé d'alimentation en combustible d'un brûleur
CH00425/14A CH707282B1 (de) 2011-09-22 2011-09-22 Brenner und Verfahren zur Brennstoffzufuhr zu einem Brenner.
DE112011105655.9T DE112011105655B4 (de) 2011-09-22 2011-09-22 Brenner und Verfahren zur Brennstoffzufuhr zu einem Brenner
US14/344,336 US9388987B2 (en) 2011-09-22 2011-09-22 Combustor and method for supplying fuel to a combustor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/RU2011/000724 WO2013043076A1 (fr) 2011-09-22 2011-09-22 Brûleur et procédé d'alimentation en combustible d'un brûleur

Publications (1)

Publication Number Publication Date
WO2013043076A1 true WO2013043076A1 (fr) 2013-03-28

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PCT/RU2011/000724 WO2013043076A1 (fr) 2011-09-22 2011-09-22 Brûleur et procédé d'alimentation en combustible d'un brûleur

Country Status (5)

Country Link
US (1) US9388987B2 (fr)
JP (1) JP6050821B2 (fr)
CH (1) CH707282B1 (fr)
DE (1) DE112011105655B4 (fr)
WO (1) WO2013043076A1 (fr)

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EP2808611A1 (fr) * 2013-05-31 2014-12-03 Siemens Aktiengesellschaft Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion
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WO2015037295A1 (fr) * 2014-06-12 2015-03-19 川崎重工業株式会社 Chambre de combustion de turbine à gaz polycarburant
US20150275755A1 (en) * 2012-12-13 2015-10-01 Kawasaki Jukogyo Kabushiki Kaisha Multi-fuel-capable gas turbine combustor
WO2015147951A2 (fr) 2014-01-24 2015-10-01 United Technologies Corporation Chambre de combustion axiale à injecteur de carburant principal restreint
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JP2017524888A (ja) * 2014-06-26 2017-08-31 シーメンス エナジー インコーポレイテッド 排気再循環を伴う軸方向段構造燃焼システム
EP3220054A1 (fr) * 2016-03-15 2017-09-20 General Electric Company Injecteurs d'air et de combustible étagés dans des systèmes de combustion de turbines à gaz
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WO2018011827A1 (fr) 2016-07-15 2018-01-18 Indian Institute Of Technology (Iit Madras) Concept d'injection directe pauvre à maillage de tourbillonnement destiné au maintien de flamme répartie à faibles émissions de polluants et à l'atténuation d'instabilité de combustion
WO2018026381A1 (fr) * 2016-08-03 2018-02-08 Siemens Aktiengesellschaft Système de combustion avec ensembles injecteurs conçus pour recapturer l'air de refroidissement dans une paroi de chambre de combustion pour former un flux d'air de protection dans un étage de combustion
EP3479025B1 (fr) * 2016-08-03 2021-11-03 Siemens Energy Global GmbH & Co. KG Ensembles injecteurs conçus pour former un flux de protection d'air injecté dans un étage de combustion dans un moteur de turbine à gaz
US10739003B2 (en) 2016-10-03 2020-08-11 United Technologies Corporation Radial fuel shifting and biasing in an axial staged combustor for a gas turbine engine
JP7023051B2 (ja) * 2017-03-23 2022-02-21 三菱重工業株式会社 ガスタービン燃焼器及び発電システム
US10982593B2 (en) * 2017-06-16 2021-04-20 General Electric Company System and method for combusting liquid fuel in a gas turbine combustor with staged combustion
US11187415B2 (en) 2017-12-11 2021-11-30 General Electric Company Fuel injection assemblies for axial fuel staging in gas turbine combustors
US11137144B2 (en) * 2017-12-11 2021-10-05 General Electric Company Axial fuel staging system for gas turbine combustors
US10816203B2 (en) 2017-12-11 2020-10-27 General Electric Company Thimble assemblies for introducing a cross-flow into a secondary combustion zone
CN108375081B (zh) * 2018-03-06 2023-08-08 哈尔滨广瀚燃气轮机有限公司 一种以燃油和天然气为燃料的双燃料环管型燃烧室
US11255543B2 (en) * 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
US11846426B2 (en) 2021-06-24 2023-12-19 General Electric Company Gas turbine combustor having secondary fuel nozzles with plural passages for injecting a diluent and a fuel
WO2024084808A1 (fr) * 2022-10-21 2024-04-25 三菱重工業株式会社 Cylindre de combustion de turbine à gaz, chambre de combustion de turbine à gaz et turbine à gaz
JP2024142595A (ja) * 2023-03-30 2024-10-11 三菱重工業株式会社 ガスタービン燃焼器

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US9388987B2 (en) 2016-07-12
JP6050821B2 (ja) 2016-12-21
US20140338359A1 (en) 2014-11-20

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